US6575697B1 - Device for fixing a turbine ferrule - Google Patents

Device for fixing a turbine ferrule Download PDF

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Publication number
US6575697B1
US6575697B1 US09/868,902 US86890201A US6575697B1 US 6575697 B1 US6575697 B1 US 6575697B1 US 86890201 A US86890201 A US 86890201A US 6575697 B1 US6575697 B1 US 6575697B1
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US
United States
Prior art keywords
spacer
ring
mortise
tenon
rim
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US09/868,902
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English (en)
Inventor
Jean-Baptiste Arilla
Sylvie Coulon
Pierre Debeneix
Florence Irène Noëlle Leutard
Paul Rodrigues
Patrice Jean Marc Rosset
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Assigned to SNECMA MOTEURS reassignment SNECMA MOTEURS ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ARILLA, JEAN-BAPTISTE, COULON, SYLVIE, DEBENEIX, PIERRE, LEUTARD, FLORENCE IRENE NOELLE, RODRIGUES, PAUL, ROSSET, PATRICE JEAN MARC
Application granted granted Critical
Publication of US6575697B1 publication Critical patent/US6575697B1/en
Assigned to SNECMA reassignment SNECMA CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SNECMA MOTEURS
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SNECMA
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Assignors: SNECMA
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • This invention pertains to a particular joint between a turbine ring, which has the function of edging the turbine by delimiting the gas flow stream, and a part called spacer which belongs to the structure of the turbine.
  • a modern joint is described in U.S. Pat. No. 5,197,853 and illustrated in FIG. 4.
  • a turbine body 1 bears a spacer 2 which itself bears a ring 3 .
  • the jointing parts of the ring 3 with the spacer 2 comprise, upstream, a spacer hook 4 and a ring hook 5 which are fitted into one another: mounting of the ring 3 is performed by pushing the end of the ring hook 5 into the recess of the spacer hook 4 , then pivoting the ring 3 so as to approach its opposite end, located downstream, to that of the spacer 2 ; the other jointing parts 6 are located on these downstream ends.
  • a spacer rim 7 first directed radially inwards, then downstream, and a ring rim 8 , directed radially outwards then axially downstream;
  • the ring rim 8 is formed as a circular groove forming a mortise 9 opening radially outwards in which is accommodated a portion of the spacer rim 7 , which thus plays the role of a tenon, formed as a rib extending radially inwards.
  • the end of the tenon has two parallel flanges 10 and 11 and they come and abut against the bottom of the mortise 9 .
  • Clips 12 are then fixed over the parallel ends of rims 7 and 8 , so that its legs 13 and 14 clasp them and prevent them from coming apart.
  • the sealing between a chamber 17 surrounded by the spacer 3 and the outside is established downstream by the contact of cylindrical surfaces formed at the end of the flanges 10 and 11 and at the bottom of the mortise 9 , and an axial play in the motion of ring 3 in spacer 2 remains around the spacer rim 7 , between the flanks of the mortise 9 .
  • the axial play creates an air leak downstream from the system, but however it must remain in order to maintain the mounting of the ring by a swinging movement.
  • U.S. Pat. No. 5,669,757 relates to an enhancement of this layout, wherein the mortise is located on the spacer rim and its downstream flank is borne by a removable annular angle, and the tenon is located on the ring rim: mounting of the ring may then be performed by a purely axial movement and the distance between the upstream end of the ring and an adjacent ring may be reduced as no swinging movement can produce a blocking at this location. The angle is then inserted with a radial movement into a groove of the spacer support in order to close the mortise and the fastening clips are finally introduced under the rims and the angle in order to maintain the latter in place.
  • This enhancement has no reinforcing effect on the seal downstream as an axial play of the tenon in the mortise remains, either by design or as a consequence of deformations undergone by the relatively flexible angle and easy to swing when the angle pushes it downstream.
  • the clips have then the extra function of opposing movements of the angle, which they are unable to do completely but this requires that they be given a circular extension of a complete turn.
  • the actual presence of the angle which is an extra part, reduces the mechanical strength of the joint and makes it manufacturing complicated.
  • the invention relates to an enhanced joint between a turbine ring and its spacer, wherein the basics of this prior joint are substantially reinstated (fixation in the radial direction by hooks fitted together on one side, and by abutment faces of concentric rims on the other side; and limitation of the axial movement by a mortise and tenon system on this other side), but is superior as regards the cohesion of the fit, the protection of the spacer against excessive heatings and the mechanical strength.
  • the clips which keep the rims clamped may have their core accommodated in the notches of these rims, which does not effect in any way the seal of the joint as the rims are separated at the location of the notches; but by pushing the cores of the clips towards the notches, their protruding outside the rims is prevented and the bulk size of the whole is thereby reduced; furthermore, the clips are used from now on for limiting the angular slipping movement of the rings of the spacer, by abutting against the side faces of the notches. So the pins of the prior realization and their bores which were the center of significant stress concentrations may therefore be suppressed.
  • the notches are also responsible for the stress concentrations but which are less significant, because of their dimensions and their more regular shape.
  • the presence of the tenon on the ring is also advantageous, as generally the ring is made in monocrystalline material which is rather difficult to machine; it is seen that it is less difficult to produce a tenon than a mortise.
  • the spacer is generally built in a material which is easier to machine, so that the mortise may be produced easily thereon, for example by forming a tab thereon, which contributes to surrounding the mortise in connection with an adjacent portion of the spacer.
  • the ring hook may cover the spacer hook, unlike the prior design, which here again, also has the advantage of locally protecting the spacer from heatings produced by the stream.
  • FIG. 1 is a general view of the invention
  • FIG. 2 is a detail of FIG. 1,
  • FIG. 3 is a perspective view of the parts of FIG. 2, and
  • FIG. 4 already described, illustrates the prior art.
  • FIG. 1 will now be discussed.
  • the spacer and the ring the individual general shape of which remains similar to that of the known realization, here bear the respective reference numbers 102 and 103 . They are conventionally formed of joined end-to-end segments along a circumference and the segments of the ring 103 bear lamellar gaskets 30 laid between the segments in order to limit gas flows in the radial and axial directions.
  • a ventilation interior chamber 31 analogous to chamber 17 is delimited by the spacer 102 and ring 103 .
  • spacer 102 bears a hook 32 , the stem 33 of which, extending radially inwards, gives into the chamber 31 and the end 34 of which extends upstream; the hook 35 of the ring 103 extends outside the latter and covers it, with a stem 36 arriving in front of its end 34 and an end 37 arriving in front of stem 33 ; the hooks are thus inverted as compared with the prior design, but their joining by fitting into each other remains the same.
  • spacer 102 and ring 103 are provided with rims 38 and 39 which extend in parallel downstream like the rims 7 and 8 of the prior design, but here the rim 38 of spacer 102 only comprises a flange 40 which establishes the abutment and the seal with a concentric flange of the rim 39 ; rims 38 and 39 are separated on the major portion of their length by play 57 .
  • the clamping of the ring 103 on spacer 102 in the axial direction is due to a tenon 41 established on the ring 103 and located upstream from the rim 38 of the spacer 102 , on the side of the ventilation chamber 31 ; this tenon is retained in a mortise 42 , delimited by the rim 38 and especially by a curved tab 43 , built on the rear face of this rim 38 .
  • the edge 44 of the tab 43 is flexible, so that it may bend when mounting is performed, in order to suppress play in the axial direction of the tenon 41 between rim 38 and tab 43 ; the low stiffness of the end 44 is such that moderate stresses may be introduced therein, which are not likely to become excessive during operation, when expansions and vibrations which are difficult to assess, have affected the joint.
  • Clips 45 are encountered once more, their legs 46 and 47 are used for tightening rims 38 and 39 together in order to maintain the abutment of flange 40 ;
  • rims 38 and 39 are provided with notches 48 and 49 facing each other and sufficiently wide so that the central core 50 of the clip 45 may be slipped therein by pushing it upstream.
  • the core 50 thus limits the angular movement of the ring 103 on the spacer 102 by means of abutments between the core 50 and the side faces 51 , 52 , 53 and 54 of the notches 48 and 49 .
  • Other means are no longer required for stopping these movements: the pins formerly used and slipped into the bores of the rims become unnecessary and are omitted.
  • a sealing gasket 55 may be inserted in a groove 56 cut out in one of the rims 39 , at the location of the abutment faces, in order to enhance the seal there.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
US09/868,902 1999-11-10 2000-11-09 Device for fixing a turbine ferrule Expired - Lifetime US6575697B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR99.14103 1999-11-10
FR9914103A FR2800797B1 (fr) 1999-11-10 1999-11-10 Assemblage d'un anneau bordant une turbine a la structure de turbine
PCT/FR2000/003126 WO2001034946A1 (fr) 1999-11-10 2000-11-09 Dispositif de fixation pour une virole de turbine

Publications (1)

Publication Number Publication Date
US6575697B1 true US6575697B1 (en) 2003-06-10

Family

ID=9551941

Family Applications (1)

Application Number Title Priority Date Filing Date
US09/868,902 Expired - Lifetime US6575697B1 (en) 1999-11-10 2000-11-09 Device for fixing a turbine ferrule

Country Status (11)

Country Link
US (1) US6575697B1 (ru)
EP (1) EP1099826B1 (ru)
JP (1) JP4181323B2 (ru)
KR (1) KR100724779B1 (ru)
CA (1) CA2359049C (ru)
DE (1) DE60017676T2 (ru)
ES (1) ES2232397T3 (ru)
FR (1) FR2800797B1 (ru)
RU (1) RU2256082C2 (ru)
UA (1) UA67818C2 (ru)
WO (1) WO2001034946A1 (ru)

Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020048512A1 (en) * 2000-10-19 2002-04-25 Snecma Moteurs Linking arrangement of a turbine stator ring to a support strut
US20020053837A1 (en) * 2000-11-09 2002-05-09 Snecma Moteurs Stator ring ventilation assembly
US20040219009A1 (en) * 2003-03-06 2004-11-04 Snecma Moteurs Turbomachine with cooled ring segments
US20050129499A1 (en) * 2003-12-11 2005-06-16 Honeywell International Inc. Gas turbine high temperature turbine blade outer air seal assembly
EP1586743A1 (fr) * 2004-04-15 2005-10-19 Snecma Anneau de turbine
EP1717418A1 (fr) * 2005-04-27 2006-11-02 Snecma Dispositif d'étanchéité pour une enceinte d'une turbomachine et moteur d'aéronef équipé de celui-ci
FR2887920A1 (fr) * 2005-06-29 2007-01-05 Snecma Dispositif de fixation de secteurs d'anneau sur un carter de turbine
US20080050224A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
US20080050225A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
US20080260524A1 (en) * 2005-03-24 2008-10-23 Alstom Technology Ltd Heat shield for sealing a flow channel of a turbine engine
US20090123280A1 (en) * 2007-11-13 2009-05-14 Snecma Turbine or compressor stage for a turbomachine
US20090202345A1 (en) * 2006-02-14 2009-08-13 Mitsubishi Heavy Industries, Ltd. Casing and fluid machine
US20090285679A1 (en) * 2008-05-16 2009-11-19 Snecma Asymmetrical member for locking ring sectors to a turbine engine casing
US20100284811A1 (en) * 2009-01-28 2010-11-11 Snecma Turbine shroud ring with rotation proofing recess
US20110121150A1 (en) * 2008-05-16 2011-05-26 Snecma Unit for locking ring sectors on a turbomachine casing, comprising radial passages for gripping it
CN102272419A (zh) * 2009-03-09 2011-12-07 斯奈克玛 涡轮环组件
US8182216B2 (en) 2006-12-27 2012-05-22 Techspace Aero Connecting system with jaws of two ferrules, including a compressor
CN102630268A (zh) * 2009-11-25 2012-08-08 斯奈克玛 与相对应的环形段绝缘的涡轮发动机外壳的环形凸缘
US20130272870A1 (en) * 2012-04-17 2013-10-17 General Electric Company Mica-based seals for gas turbine shroud retaining clip
WO2013163554A1 (en) * 2012-04-27 2013-10-31 General Electric Company Retaining clip, turbine frame, and method of limiting radial movement
US20150016970A1 (en) * 2011-12-31 2015-01-15 Rolls-Royce North American Technologies, Inc. Blade track assembly, components, and methods
US20150071769A1 (en) * 2013-09-06 2015-03-12 MTU Aero Engines AG Method for disassembly and assembly of a rotor of a gas turbine
US20150132054A1 (en) * 2012-04-27 2015-05-14 General Electric Company System and method of limiting axial movement between components in a turbine assembly
US9416672B2 (en) 2012-10-12 2016-08-16 MTU Aero Engines AG Housing structure with improved seal and cooling
US9581039B2 (en) 2010-03-02 2017-02-28 Snecma Fiber preform for a turbine ring sector, and its method of fabrication
US9745854B2 (en) 2012-04-27 2017-08-29 General Electric Company Shroud assembly and seal for a gas turbine engine
US9828879B2 (en) 2015-05-11 2017-11-28 General Electric Company Shroud retention system with keyed retention clips
CN107735549A (zh) * 2015-05-22 2018-02-23 赛峰航空器发动机 由法兰支撑的涡轮机环组件
CN107810310A (zh) * 2015-05-22 2018-03-16 赛峰航空器发动机 以爪形离合器方式保持的涡轮环组件
US9932901B2 (en) 2015-05-11 2018-04-03 General Electric Company Shroud retention system with retention springs
US10450895B2 (en) * 2016-04-22 2019-10-22 United Technologies Corporation Stator arrangement
DE102018210597A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Leitschaufelanordnung für eine strömungsmaschine
US20200025011A1 (en) * 2018-07-18 2020-01-23 United Technologies Corporation Blade outer air seal aft hook retainer
US10557365B2 (en) 2017-10-05 2020-02-11 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having reaction load distribution features
US10634010B2 (en) 2018-09-05 2020-04-28 United Technologies Corporation CMC BOAS axial retaining clip
US10697314B2 (en) 2016-10-14 2020-06-30 Rolls-Royce Corporation Turbine shroud with I-beam construction
US20200362717A1 (en) * 2019-05-15 2020-11-19 United Technologies Corporation Cmc boas arrangement
US11021988B2 (en) * 2017-03-16 2021-06-01 Safran Aircraft Engines Turbine ring assembly
US11149563B2 (en) 2019-10-04 2021-10-19 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having axial reaction load distribution features
US11149574B2 (en) 2017-09-06 2021-10-19 Safran Aircraft Engines Turbine assembly with ring segments

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US7600967B2 (en) * 2005-07-30 2009-10-13 United Technologies Corporation Stator assembly, module and method for forming a rotary machine
FR2921410B1 (fr) * 2007-09-24 2010-03-12 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des moyens permettant sa prehension
FR2923528B1 (fr) * 2007-11-13 2009-12-11 Snecma Etage de turbine ou de compresseur d'un turboreacteur
FR2923527B1 (fr) * 2007-11-13 2013-12-27 Snecma Etage de turbine ou de compresseur, en particulier de turbomachine
FR2931197B1 (fr) * 2008-05-16 2010-06-18 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages axiaux pour sa prehension
US8118548B2 (en) * 2008-09-15 2012-02-21 General Electric Company Shroud for a turbomachine
FR2942845B1 (fr) * 2009-03-09 2011-04-01 Snecma Ensemble d'anneau de turbine
FR2942844B1 (fr) * 2009-03-09 2014-06-27 Snecma Ensemble d'anneau de turbine avec arret axial
FR2955359B1 (fr) * 2010-01-21 2013-07-19 Snecma Etancheite amont d'un anneau en cmc d'un etage de turbine
FR2955898B1 (fr) * 2010-02-02 2012-10-26 Snecma Etancheite amont d'un anneau en cmc dans une turbine de turbomachine
FR3009739B1 (fr) * 2013-08-13 2015-09-11 Snecma Amelioration pour le verrouillage de pieces de support d'aubage
FR3009740B1 (fr) 2013-08-13 2017-12-15 Snecma Amelioration pour le verrouillage de pieces de support d'aubage
RU2657404C1 (ru) * 2017-06-16 2018-06-13 Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Разъемный корпус турбомашины
US11933221B2 (en) * 2021-10-21 2024-03-19 Rtx Corporation Tongue joint including mating channel for cooling

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Cited By (75)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6699011B2 (en) * 2000-10-19 2004-03-02 Snecma Moteurs Linking arrangement of a turbine stator ring to a support strut
US20020048512A1 (en) * 2000-10-19 2002-04-25 Snecma Moteurs Linking arrangement of a turbine stator ring to a support strut
US20020053837A1 (en) * 2000-11-09 2002-05-09 Snecma Moteurs Stator ring ventilation assembly
US6896038B2 (en) * 2000-11-09 2005-05-24 Snecma Moteurs Stator ring ventilation assembly
US20040219009A1 (en) * 2003-03-06 2004-11-04 Snecma Moteurs Turbomachine with cooled ring segments
US7011493B2 (en) 2003-03-06 2006-03-14 Snecma Moteurs Turbomachine with cooled ring segments
US20050129499A1 (en) * 2003-12-11 2005-06-16 Honeywell International Inc. Gas turbine high temperature turbine blade outer air seal assembly
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly
US20090074579A1 (en) * 2004-04-15 2009-03-19 Snecma Moteurs Turbine ring
EP1586743A1 (fr) * 2004-04-15 2005-10-19 Snecma Anneau de turbine
FR2869070A1 (fr) * 2004-04-15 2005-10-21 Snecma Moteurs Sa Anneau de turbine
US7513740B1 (en) 2004-04-15 2009-04-07 Snecma Turbine ring
US20080050225A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
US20080050224A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
US7658593B2 (en) 2005-03-24 2010-02-09 Alstom Technology Ltd Heat accumulation segment
US20080260524A1 (en) * 2005-03-24 2008-10-23 Alstom Technology Ltd Heat shield for sealing a flow channel of a turbine engine
US7665957B2 (en) 2005-03-24 2010-02-23 Alstom Technology Ltd Heat shield for sealing a flow channel of a turbine engine
US7665958B2 (en) 2005-03-24 2010-02-23 Alstom Technology Ltd. Heat accumulation segment
FR2885168A1 (fr) * 2005-04-27 2006-11-03 Snecma Moteurs Sa Dispositif d'etancheite pour une enceinte d'une turbomachine, et moteur d'aeronef equipe de celui-ci
US20060245924A1 (en) * 2005-04-27 2006-11-02 Snecma Sealing device for a chamber of a turbomachine, and aircraft engine equipped with said sealing device
EP1717418A1 (fr) * 2005-04-27 2006-11-02 Snecma Dispositif d'étanchéité pour une enceinte d'une turbomachine et moteur d'aéronef équipé de celui-ci
US7594792B2 (en) 2005-04-27 2009-09-29 Snecma Sealing device for a chamber of a turbomachine, and aircraft engine equipped with said sealing device
FR2887920A1 (fr) * 2005-06-29 2007-01-05 Snecma Dispositif de fixation de secteurs d'anneau sur un carter de turbine
US20090202345A1 (en) * 2006-02-14 2009-08-13 Mitsubishi Heavy Industries, Ltd. Casing and fluid machine
US8118551B2 (en) 2006-02-14 2012-02-21 Mitsubishi Heavy Industries, Ltd. Casing and fluid machine
US8182216B2 (en) 2006-12-27 2012-05-22 Techspace Aero Connecting system with jaws of two ferrules, including a compressor
RU2490477C2 (ru) * 2007-11-13 2013-08-20 Снекма Ступень турбомашины, турбина, компрессор и турбомашина, содержащие такую ступень
US20090123280A1 (en) * 2007-11-13 2009-05-14 Snecma Turbine or compressor stage for a turbomachine
US8277179B2 (en) * 2007-11-13 2012-10-02 Snecma Turbine or compressor stage for a turbomachine
US8721277B2 (en) * 2008-05-16 2014-05-13 Snecma Unit for locking ring sectors on a turbomachine casing, comprising radial passages for gripping it
US20110121150A1 (en) * 2008-05-16 2011-05-26 Snecma Unit for locking ring sectors on a turbomachine casing, comprising radial passages for gripping it
US20090285679A1 (en) * 2008-05-16 2009-11-19 Snecma Asymmetrical member for locking ring sectors to a turbine engine casing
US8167552B2 (en) * 2008-05-16 2012-05-01 Snecma Asymmetrical member for locking ring sectors to a turbine engine casing
US20100284811A1 (en) * 2009-01-28 2010-11-11 Snecma Turbine shroud ring with rotation proofing recess
US8425184B2 (en) * 2009-01-28 2013-04-23 Snecma Turbine shroud ring with rotation proofing recess
CN102272419A (zh) * 2009-03-09 2011-12-07 斯奈克玛 涡轮环组件
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DE60017676D1 (de) 2005-03-03
FR2800797B1 (fr) 2001-12-07
RU2256082C2 (ru) 2005-07-10
CA2359049A1 (fr) 2001-05-17
EP1099826B1 (fr) 2005-01-26
EP1099826A1 (fr) 2001-05-16
DE60017676T2 (de) 2005-12-29
JP2003514182A (ja) 2003-04-15
ES2232397T3 (es) 2005-06-01
UA67818C2 (ru) 2004-07-15
KR100724779B1 (ko) 2007-06-04
CA2359049C (fr) 2009-01-13
WO2001034946A1 (fr) 2001-05-17
KR20010089800A (ko) 2001-10-08
FR2800797A1 (fr) 2001-05-11
JP4181323B2 (ja) 2008-11-12

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